CN114412577B - Turbine moving blade - Google Patents
Turbine moving blade Download PDFInfo
- Publication number
- CN114412577B CN114412577B CN202210081620.7A CN202210081620A CN114412577B CN 114412577 B CN114412577 B CN 114412577B CN 202210081620 A CN202210081620 A CN 202210081620A CN 114412577 B CN114412577 B CN 114412577B
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- blade
- cooling
- chamber
- turbine
- channels
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- 238000001816 cooling Methods 0.000 claims abstract description 138
- 239000002826 coolant Substances 0.000 claims abstract description 21
- 238000004891 communication Methods 0.000 claims description 10
- 230000000903 blocking effect Effects 0.000 claims description 3
- 239000000463 material Substances 0.000 abstract description 3
- 239000007789 gas Substances 0.000 description 5
- 230000035882 stress Effects 0.000 description 4
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
Abstract
The application relates to the technical field of turbine blade cooling, in particular to a turbine movable blade long blade. The blade body of the turbine movable blade meets the following conditions: h is more than or equal to 2L; h is the height of the blade body, and L is the maximum width of the blade body. The inside of turbine movable vane long blade is provided with the cooling structure who is used for supplying the coolant medium circulation, and cooling structure is located turbine movable vane long blade's latter half, and cooling structure satisfies: m is less than or equal to 0.5H; m is the maximum height of the part of the cooling structure inside the blade body. This application is through setting up cooling structure in the lower half of turbine movable vane long blade, makes the maximum height of cooling structure inside the blade body of turbine movable vane long blade not more than half of blade body height to carry out cooling to the great lower half of stress of turbine movable vane long blade, satisfy turbine movable vane long blade's cooling demand, avoided simultaneously removing the cooling runner of inside material in order to form cooling structure at blade body half and influence the intensity and the life of blade.
Description
Technical Field
The application relates to the technical field of turbine blade cooling, in particular to a turbine movable blade long blade.
Background
Turbine blades of gas turbines or aeroengines operate in high temperature and high pressure environments, and the gas inlet temperature exceeds the temperature that can be tolerated by metallic materials, so blades with hollow cooling structures are indispensable; the hollow cooling structure of the blade is designed with the following limitations: firstly, the cold air needs to be saved, and the efficiency of the unit is improved; secondly, the air-cooled blade is matched with the pneumatic shape of the blade, so that the influence of the hollow cooling structure on the strength of the blade is reduced to the greatest extent; thirdly, the convenience of the manufacturing process ensures the feasibility of the process and the cost control.
For the 1-2-stage movable blades of the turbine, the bearing temperature is high, the omnibearing cooling is required, and as the 1-2-stage movable blades are generally short blades, the maximum thickness of the blade profile and the thickness of the tail edge of the blade body are thicker, and the hollow cooling structure is suitable for being arranged in the hollow cooling structure.
However, for the long turbine blade, the temperature of the fuel gas is reduced greatly after the long turbine blade is positioned at the third stage, the cooling requirement is not required to be too high, the maximum thickness of the blade profile and the thickness of the tail edge of the long turbine blade are very thin, the blade tip also has obvious tendency of shrinking and thinning, and the relatively complex hollow cooling structure arranged inside the 1-2-stage movable blade is difficult to arrange in the long turbine blade without affecting the strength and the service life of the blade.
Disclosure of Invention
The invention aims to provide a turbine movable vane long vane with a hollow cooling structure.
The invention provides a turbine movable blade, which comprises a blade root, a blade platform and a blade body; the long turbine blade is provided with a cooling structure, and the cooling structure comprises a cooling flow passage formed inside the long turbine blade and used for circulating cooling medium;
the cooling structure is positioned on the lower half part of the turbine blade towards the blade root, and part of the cooling structure is positioned inside the blade body;
the blade body meets the following conditions: h is more than or equal to 2L, and the cooling structure meets the following conditions: m is less than or equal to 0.5H;
wherein H is the height of the blade body, L is the maximum width of the blade body, and M is the maximum height of the cooling structure in the blade body.
Further, the cooling structure comprises an air inlet chamber, a cooling chamber and an air outlet chamber;
one side of the blade body in the width direction is a blade front edge, and the other side of the blade body in the width direction is a blade tail edge;
the air inlet chamber is positioned on one side of the turbine movable blade close to the front edge of the blade, and the air outlet chamber is positioned on one side of the turbine movable blade close to the tail edge of the blade;
the cooling chamber is positioned between the air inlet chamber and the air outlet chamber, and the air inlet chamber is communicated with the air outlet chamber through the cooling chamber;
the inner spaces of the air inlet chamber, the cooling chamber and the air outlet chamber form the cooling flow passage;
the cooling structure is characterized in that an air inlet communicated with the air inlet cavity is formed on the body of the turbine movable vane long blade, and an air outlet communicated with the air outlet cavity is formed on the body of the turbine movable vane long blade.
Further, the air inlet is located on the blade root, and the air outlet is located on the blade platform.
Further, the air inlet chamber is positioned on one side of the cooling chamber facing the blade root of the turbine movable blade, and the one side of the cooling chamber facing the blade root is communicated with the air inlet chamber;
and a blocking part is formed between the air outlet cavity and the cooling cavity, and one end, far away from the blade root, of the cooling cavity is communicated with the air outlet cavity.
Further, the air inlet chamber is positioned at one side of the cooling chamber facing the front edge of the blade, and one side of the cooling chamber facing the front edge of the blade is communicated with the air inlet chamber;
the air outlet chamber is positioned on one side of the cooling chamber facing the tail edge of the blade, and one side of the cooling chamber facing the tail edge of the blade is communicated with the air outlet chamber.
Further, the cooling chamber includes a plurality of first passages spaced apart from each other and parallel to each other, the plurality of first passages communicating with each other;
at least one of the first plurality of channels is in communication with the inlet chamber and at least one of the first plurality of channels is in communication with the outlet chamber.
Further, the cooling chamber includes a plurality of second channels spaced apart from each other and parallel to each other;
the two sides of the blade body in the thickness direction are respectively a blade basin side and a blade back side, a plurality of first channels are positioned on one side close to the blade basin side, and a plurality of second channels are positioned on one side close to the blade back side;
the plurality of second channels are communicated with each other, at least one of the plurality of second channels is communicated with the air inlet chamber, and at least one of the plurality of second channels is communicated with the air outlet chamber.
Further, a predetermined angle is formed between the length extension direction of the first channels and the length extension direction of the second channels, so that the first channels and the second channels are intersected with each other;
at least one of the first channels communicates with one of the second channels at a channel end.
Further, the first and second channels, which arbitrarily intersect each other, communicate at an intersection.
Further, an included angle β between the extending direction of the first channel and the width direction of the blade body satisfies: beta is more than or equal to 5 degrees and less than or equal to 85 degrees.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a turbine movable blade, which comprises a blade root, a blade body and a blade platform, wherein the blade body has a preset height and a preset maximum width, and the blade body meets the following conditions: h is more than or equal to 2L; wherein H is the height of the blade body, L is the maximum width of the blade body, namely the blade body of the long blade of the turbine rotor blade meets the condition that the height of the blade body is more than or equal to 2 times of the maximum width of the blade body. The inside of turbine movable vane long blade is provided with cooling structure, and cooling structure includes cooling runner, and cooling runner forms in the inside of turbine movable vane long blade, and cooling runner is used for supplying the coolant circulation. The cooling structure is located in the interior of the lower half of the turbine movable blade towards the blade root, and the cooling structure satisfies: m is less than or equal to 0.5H; where M is the maximum height of the part of the cooling structure inside the blade body and H is the height of the blade body.
This application is through setting up cooling structure in the lower half of turbine movable vane long blade, makes the maximum height of cooling structure inside the blade body of turbine movable vane long blade not more than half of blade body height to carry out cooling to the great lower half of stress of turbine movable vane long blade, satisfy turbine movable vane long blade's cooling demand, avoided simultaneously removing the cooling runner of inside material in order to form cooling structure at blade body half and influence the intensity and the life of blade.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a long turbine bucket with a cooling structure according to an embodiment of the present invention at a first view angle;
FIG. 2 is a schematic view of a turbine bucket with a cooling structure according to an embodiment of the present invention at a second view angle;
FIG. 3 is a schematic cross-sectional view taken along line A-A of FIG. 2;
FIG. 4 is a schematic view of one cooling structure of FIG. 1;
FIG. 5 is a schematic view of a turbine bucket having yet another cooling configuration according to an embodiment of the present invention at a first view angle;
fig. 6 is a schematic view of still another cooling structure in fig. 5.
Reference numerals:
1-turbine blade, 11-blade body, 111-blade back side, 112-blade basin side, 113-blade leading edge, 114-blade trailing edge, 12-blade platform, 13-blade root, 2-cooling structure, 21-inlet chamber, 22-outlet chamber, 23-cooling chamber, 231-first channel, 232-second channel, 24-inlet port, 25-outlet port.
Detailed Description
The following description of the embodiments of the present invention will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown.
The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention.
All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Turbine bucket blades according to some embodiments of the present application are described below with reference to fig. 1-6.
As shown in fig. 1 and 2, the present application provides a turbine blade 1, which includes a blade root 13, a blade body 11 and a blade platform 12, wherein the blade root 13 is disposed on one side of the blade platform 12, and the blade body 11 is disposed on the other side of the blade platform 12; for example, the blade root 13 and the blade body 11 are integrally formed on both sides of the blade platform 12, respectively. The blade body 11 has a predetermined height and maximum width, and the blade body 11 satisfies: h is more than or equal to 2L; wherein H is the height of the blade body 11, L is the maximum width of the blade body 11, namely the blade body 11 of the turbine movable blade 1 satisfies that the height of the blade body 11 is more than or equal to 2 times of the maximum width of the blade body 11.
The inside of turbine movable vane long blade 1 is provided with cooling structure 2, and cooling structure 2 includes the cooling runner, and the cooling runner forms in the inside of turbine movable vane long blade 1, and the cooling circulation is used for supplying the coolant circulation, and coolant such as air to carry out the heat exchange with turbine movable vane long blade 1 through coolant, thereby realize cooling down to turbine movable vane long blade 1.
As shown in fig. 1 and 2, one end of the long turbine blade 1 provided with the blade root 13 is a lower end of the long turbine blade 1 in the height direction, the other end is an upper end of the long turbine blade 1 in the height direction, and the cooling structure 2 is positioned in the lower half part of the long turbine blade 1 facing the blade root 13; part of the cooling structure 2 is located inside the blade body 11, and the cooling structure 2 satisfies: m is less than or equal to 0.5H; wherein M is the maximum height of the part of the cooling structure 2 in the blade body 11, H is the height of the blade body 11, namely, the maximum height of the cooling structure 2 in the blade body 11 is not more than half of the height of the blade body 11, and when a cooling medium flows in the cooling structure 2, the lower half part of the turbine movable blade 1 can be cooled.
For the turbine movable vane 1 used for the third stage and later of the gas turbine or the aeroengine, as the gas temperature of the environment where the turbine movable vane 1 is positioned is reduced greatly compared with the gas temperature of the environment where the turbine movable vane of the 1-2 stages is positioned, the cooling requirement is relatively low, the maximum thickness of the vane shape and the thickness of the tail edge of the turbine movable vane 1 are both very thin, the vane tip has obvious shrinkage tendency, and meanwhile, the main stress bearing part of the turbine movable vane 1 in use is the part with the vane shape section of less than 50 percent, and the bearing stress is relatively large; this application is through setting up cooling structure 2 in the lower half of turbine movable vane long blade 1, makes cooling structure 2 not exceeding the half of blade body 11 height at the inside maximum height of blade body 11 of turbine movable vane long blade 1 to carry out cooling to the great lower half of the stress of turbine movable vane long blade 1, on the one hand can satisfy turbine movable vane long blade 1's cooling demand, avoided blade body 11 to get rid of the cooling runner of inside material in order to form cooling structure 2 simultaneously and influence the intensity and the life of blade.
In one embodiment of the present application, preferably, as shown in fig. 2 and 3, the cooling structure 2 includes an air inlet chamber 21, a cooling chamber 23, and an air outlet chamber 22 formed inside the turbine bucket 1; one side in the width direction of the blade body 11 is a blade leading edge 113 of the blade body 11, the other side in the width direction of the blade body 11 is a blade trailing edge 114 of the blade body 11, the air inlet chamber 21 is positioned at one side of the inside of the turbine blade 1 near the blade leading edge 113, the air outlet chamber 22 is positioned at one side of the inside of the turbine blade 1 near the blade trailing edge 114, the cooling chamber 23 is positioned between the air inlet chamber 21 and the air outlet chamber 22, and the air inlet chamber 21 is communicated with the air outlet chamber 22 through the cooling chamber 23; the cooling structure 2 is formed with an air inlet 24 communicated with the air inlet chamber 21 on the body of the turbine movable vane long vane 1, the cooling structure 2 is formed with an air outlet 25 communicated with the air outlet chamber 22 on the body of the turbine movable vane long vane 1, and external cooling medium can enter the inside of the turbine movable vane long vane 1 through the air inlet 24, then flows through the air inlet chamber 21, the cooling chamber 23 and the air outlet chamber 22 in sequence, and finally flows out of the turbine movable vane long vane 1 through the air outlet 25; that is, in the cooling structure 2 having a predetermined height, the cooling medium flows from one side to the other side in the width direction of the turbine long blade 1, thereby achieving sufficient cooling of the lower half of the turbine long blade 1.
An air inlet 24 formed in the body of the turbine bucket 1 by the cooling structure 2; for example, as shown in FIG. 1, the air inlet 24 is located on the blade root 13 of the turbine bucket 1. An air outlet 25 formed in the body of the turbine bucket 1 by the cooling structure 2; for example, as shown in FIG. 1, the air outlet 25 is located on the blade platform 12 of the turbine bucket 1. That is, the surface of the blade body 11 is prevented from being perforated, thereby avoiding adverse effects on the blade strength and the service life.
In one embodiment of the present application, preferably, as shown in fig. 2 and 4, the cooling chamber 23 includes a plurality of first passages 231, the plurality of first passages 231 being spaced apart from each other in the width direction of the blade body 11 and being disposed in parallel with each other, the plurality of first passages 231 each having a height in the height direction of the turbine moving blade 1 inside the turbine moving blade; the plurality of first passages 231 communicate with each other, and at least one of the plurality of first passages 231 communicates with the air inlet chamber 21, and at least one of the plurality of first passages 231 communicates with the air outlet chamber 22; the cooling medium in the intake chamber 21 can enter the first passages 231 communicating with the intake chamber 21 and then be dispersed to all the first passages 231; the cold zone medium in the plurality of first channels 231 can be converged into the outlet chamber 22 through the first channels 231 communicating with the outlet chamber 22, and then flow out of the turbine bucket 1 via the outlet 25.
In one embodiment of the present application, it is preferable that the cooling chamber 23 further includes a plurality of second passages 232, the plurality of second passages 232 also being spaced apart from each other in the width direction of the blade body 11 and being disposed parallel to each other, the plurality of second passages 232 each having a height in the height direction of the turbine-blade long blade 1 inside the turbine-blade; as shown in fig. 3, the two sides in the thickness direction of the blade body 11 of the turbine long blade 1 are the blade basin side 112 and the blade back side 111, respectively, the plurality of first passages 231 are provided near the blade basin side 112, and the plurality of second passages 232 are provided near the blade back side 111, so that a double-layer flow passage is formed in the inside of the turbine long blade 1 along the thickness direction of the blade body 11, that is, one layer is formed by the plurality of first passages 231, and the other layer is formed by the plurality of second passages 232. The plurality of second channels 232 are in communication with each other, and at least one of the plurality of second channels 232 is in communication with the inlet chamber 21, and at least one of the plurality of second channels 232 is in communication with the outlet chamber 22; the cooling medium in the intake chamber 21 can enter into the second passages 232 communicating with the intake chamber 21 and then be dispersed to all of the second passages 232; the cold zone medium in the plurality of second channels 232 can be converged to the outlet chamber 22 through the second channels 232 communicating with the outlet chamber 22, and then flow out of the turbine bucket 1 via the outlet 25. Therefore, through setting up double-deck runner in the inside of turbine movable vane long blade 1, a plurality of first passageway 231 and a plurality of second passageway 232 promptly, increased the heat transfer area to a certain extent, make heat exchange efficiency higher, also make the heat transfer of heat transfer region more even simultaneously, reduced the influence of the thermal stress that the heat transfer inequality brought.
In one embodiment of the present application, preferably, as shown in fig. 2 and 4, the length extension direction of the plurality of first channels 231 and the length direction of the plurality of second channels 232 have a predetermined angle therebetween such that the plurality of first channels 231 and the plurality of second channels 232 cross each other; for example, the upper ends of the first plurality of channels 231 are each inclined toward one side of the blade trailing edge 114, and the upper ends of the second plurality of channels 232 are each inclined toward one side of the blade leading edge 113. At least one first channel 231 is communicated with one second channel 232, so that when the cooling medium flows in the cooling cavity 23, the cooling medium can be changed from the first channel 231 to the second channel 232 or from the second channel 232 to the first channel 231, the flow path of the cooling medium in the turbine blade 1 is increased, and the heat exchange efficiency is improved.
Preferably, as shown in fig. 2, the angle β between the length extension direction of the first passage 231 and the width direction of the blade body 11 satisfies: beta is more than or equal to 5 degrees and less than or equal to 85 degrees.
Regarding the arrangement of the cooling chamber 23, the air intake chamber 21 and the air outlet chamber 22, in one embodiment of the present application, preferably, as shown in fig. 1 and 4, the cooling chamber 23 having a complicated structure is provided at the middle of the turbine blade 1 having a large thickness and at one side of the blade leading edge 113, the air intake chamber 21 is located below the cooling chamber 23, and the lower end of the cooling chamber 23 communicates with the air intake chamber 21; the air outlet chamber 22 has a simple structure, is arranged at one side of the blade tail edge 114 of the turbine blade 1 with a thinner thickness, and a blocking part is formed between the air outlet chamber 22 and the cooling chamber 23, so that the upper end of the cooling chamber 23 is communicated with the air outlet chamber 22; therefore, the cooling medium can flow upwards into the cooling chamber 23 from the air inlet chamber 21 below, then flows into the air outlet chamber 22 from the upper end of the cooling chamber 23, flows downwards along the air outlet chamber 22 until flowing out of the turbine movable vane long blade 1, so that the cooling medium has a generally U-shaped flow trend in the interior of the turbine movable vane long blade 1, the cooling medium can effectively exchange heat for the lower half part of the turbine movable vane long blade 1, and the flow path of the medium is increased through the integral U-shaped flow trend and the turning and reversing between the first channel 231 and the second channel 232, and the heat exchange efficiency is improved.
In one embodiment of the present application, it is also preferable that the air inlet chamber 21 and the air outlet chamber 22 are provided on both sides of the cooling chamber 23 in the width direction, that is, the air inlet chamber 21 is located on the side of the cooling chamber 23 facing the blade leading edge 113, and the side of the cooling chamber 23 facing the blade leading edge 113 is communicated with the air inlet chamber 21, as shown in fig. 5 and 6; the air outlet chamber 22 is located at one side of the cooling chamber 23 facing the blade tail edge 114, and one side of the cooling chamber 23 facing the blade tail edge 114 is communicated with the air outlet chamber 22, so that the cooling medium flows from one side of the blade front edge 113 to one side of the blade tail edge 114 along the width direction of the turbine blade 1 in the interior of the turbine blade 1, effective heat exchange of the lower half of the turbine blade 1 is ensured, the flow path of the cooling medium is increased through the reversing of the cooling medium in the first channel 231 and the second channel 232, and the heat exchange efficiency is improved.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (10)
1. A turbine movable blade comprises a blade root, a blade platform and a blade body; the cooling structure is characterized in that the turbine movable vane long blade is provided with a cooling structure, and the cooling structure comprises a cooling flow passage formed inside the turbine movable vane long blade and used for circulating cooling medium;
the cooling structure is positioned on the lower half part of the turbine blade towards the blade root, and part of the cooling structure is positioned inside the blade body;
the blade body meets the following conditions: h is more than or equal to 2L, and the cooling structure meets the following conditions: m is less than or equal to 0.5H;
wherein H is the height of the blade body, L is the maximum width of the blade body, and M is the maximum height of the cooling structure in the blade body.
2. The turbine bucket of claim 1, wherein the cooling structure comprises an inlet plenum, a cooling plenum, and an outlet plenum;
one side of the blade body in the width direction is a blade front edge, and the other side of the blade body in the width direction is a blade tail edge;
the air inlet chamber is positioned on one side of the turbine movable blade close to the front edge of the blade, and the air outlet chamber is positioned on one side of the turbine movable blade close to the tail edge of the blade;
the cooling chamber is positioned between the air inlet chamber and the air outlet chamber, and the air inlet chamber is communicated with the air outlet chamber through the cooling chamber;
the inner spaces of the air inlet chamber, the cooling chamber and the air outlet chamber form the cooling flow passage;
the cooling structure is characterized in that an air inlet communicated with the air inlet cavity is formed on the body of the turbine movable vane long blade, and an air outlet communicated with the air outlet cavity is formed on the body of the turbine movable vane long blade.
3. The turbine bucket of claim 2 wherein said inlet is located on said root and said outlet is located on said bucket platform.
4. The turbine bucket of claim 2, wherein the air intake chamber is located on a side of the cooling chamber facing a root of the turbine bucket, the side of the cooling chamber facing the root being in communication with the air intake chamber;
and a blocking part is formed between the air outlet cavity and the cooling cavity, and one end, far away from the blade root, of the cooling cavity is communicated with the air outlet cavity.
5. The turbine bucket of claim 2 wherein the inlet plenum is located on a side of the cooling plenum facing the bucket leading edge, the side of the cooling plenum facing the bucket leading edge being in communication with the inlet plenum;
the air outlet chamber is positioned on one side of the cooling chamber facing the tail edge of the blade, and one side of the cooling chamber facing the tail edge of the blade is communicated with the air outlet chamber.
6. The turbine bucket of claim 2 wherein said cooling chamber comprises a plurality of first passages spaced apart from and parallel to each other, a plurality of said first passages communicating with each other;
at least one of the first plurality of channels is in communication with the inlet chamber and at least one of the first plurality of channels is in communication with the outlet chamber.
7. The turbine bucket of claim 6 wherein said cooling chamber comprises a plurality of second channels spaced apart from and parallel to each other;
the two sides of the blade body in the thickness direction are respectively a blade basin side and a blade back side, a plurality of first channels are positioned on one side close to the blade basin side, and a plurality of second channels are positioned on one side close to the blade back side;
the plurality of second channels are communicated with each other, at least one of the plurality of second channels is communicated with the air inlet chamber, and at least one of the plurality of second channels is communicated with the air outlet chamber.
8. The turbine bucket of claim 7 wherein a length extension of a plurality of said first channels and a length extension of a plurality of said second channels are at a predetermined angle therebetween such that a plurality of said first channels and a plurality of said second channels intersect one another;
at least one of the first channels communicates with one of the second channels at the end of the cooling channel.
9. The turbine bucket of claim 8 wherein said first and second channels of any interdigitation communicate at an intersection.
10. The turbine bucket of claim 8 wherein the angle β between the direction of extension of the first channel and the width of the blade satisfies: beta is more than or equal to 5 degrees and less than or equal to 85 degrees.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210081620.7A CN114412577B (en) | 2022-01-24 | 2022-01-24 | Turbine moving blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210081620.7A CN114412577B (en) | 2022-01-24 | 2022-01-24 | Turbine moving blade |
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| Publication Number | Publication Date |
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| CN114412577A CN114412577A (en) | 2022-04-29 |
| CN114412577B true CN114412577B (en) | 2024-03-15 |
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| CN202210081620.7A Active CN114412577B (en) | 2022-01-24 | 2022-01-24 | Turbine moving blade |
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|---|---|---|---|---|
| GB677052A (en) * | 1949-12-28 | 1952-08-06 | Bbc Brown Boveri & Cie | Cooled turbine rotor |
| EP1925780A1 (en) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Blade for an axial-flow turbine |
| CN102116179A (en) * | 2011-03-11 | 2011-07-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine engine |
| CN103946483A (en) * | 2011-11-25 | 2014-07-23 | 西门子公司 | Airfoil with cooling passages |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10053356A1 (en) * | 2000-10-27 | 2002-05-08 | Alstom Switzerland Ltd | Cooled component, casting core for the production of such a component, and method for producing such a component |
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2022
- 2022-01-24 CN CN202210081620.7A patent/CN114412577B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB677052A (en) * | 1949-12-28 | 1952-08-06 | Bbc Brown Boveri & Cie | Cooled turbine rotor |
| EP1925780A1 (en) * | 2006-11-23 | 2008-05-28 | Siemens Aktiengesellschaft | Blade for an axial-flow turbine |
| CN102116179A (en) * | 2011-03-11 | 2011-07-06 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Turbine rotor blade of gas turbine engine |
| CN103946483A (en) * | 2011-11-25 | 2014-07-23 | 西门子公司 | Airfoil with cooling passages |
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| CN114412577A (en) | 2022-04-29 |
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Address after: 310000 Building 1, No. 608, Kangxin Road, Linping District, Hangzhou, Zhejiang Applicant after: Hangzhou Turbine Power Group Co.,Ltd. Address before: 311100 Building 1, No. 608, Kangxin Road, economic and Technological Development Zone, Yuhang District, Hangzhou City, Zhejiang Province Applicant before: HANGZHOU STEAM TURBINE Co.,Ltd. |
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